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Research Papers

Film Cooling Parameter Waveforms on a Turbine Blade Leading Edge Model With Oscillating Stagnation Line

[+] Author and Article Information
James L. Rutledge

Department of Aeronautics and Astronautics,
Air Force Institute of Technology,
Wright-Patterson Air Force Base, OH 45433
e-mail: james.rutledge@us.af.mil

Tylor C. Rathsack, Matthew T. Van Voorhis, Marc D. Polanka

Department of Aeronautics and Astronautics,
Air Force Institute of Technology,
Wright-Patterson Air Force Base, OH 45433

1Corresponding author.

2Currently at Purdue University, West Lafayette, IN.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 3, 2015; final manuscript received December 16, 2015; published online February 17, 2016. Editor: Kenneth C. Hall.This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Approved for public release; distribution is unlimited.

J. Turbomach 138(7), 071005 (Feb 17, 2016) (12 pages) Paper No: TURBO-15-1287; doi: 10.1115/1.4032455 History: Received December 03, 2015; Revised December 16, 2015

It is necessary to understand how film cooling influences the external convective boundary condition involving both the adiabatic wall temperature and the heat transfer coefficient in order to predict the thermal durability of a gas turbine hot gas path component. Most studies in the past have considered only steady flow, but studies of the unsteadiness naturally present in turbine flow have become more prevalent. One source of unsteadiness is wake passage from upstream components which can cause fluctuations in the stagnation location on turbine airfoils. This in turn causes unsteadiness in the behavior of the leading edge coolant jets and thus fluctuations in both the adiabatic effectiveness and heat transfer coefficient. The dynamics of h and η are now quantifiable with modern inverse heat transfer methods and nonintrusive infrared thermography. The present study involved the application of a novel inverse heat transfer methodology to determine time-resolved adiabatic effectiveness and heat transfer coefficient waveforms on a simulated turbine blade leading edge with an oscillating stagnation position. The leading edge geometry was simulated with a circular cylinder with a coolant hole located 21.5 deg downstream from the leading edge stagnation line, angled 20 deg to the surface and 90 deg to the streamwise direction. The coolant plume is shown to shift in response to the stagnation line movement. These oscillations thus influence the film cooling coverage, and the time-averaged benefit of film cooling is influenced by the oscillation.

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References

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Figures

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Fig. 1

Leading edge model

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Fig. 2

Right-handed coordinate system

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Fig. 3

Schematic of test facility

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Fig. 4

Fixed and rotating blockages used to cause stagnation line oscillation

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Fig. 5

Flowchart showing steps to conduct experiment and reduce data in accordance with IFSAW algorithm

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Fig. 6

Adiabatic effectiveness: steady film cooling, M = 0.5 [23]

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Fig. 7

Adiabatic effectiveness: steady film cooling, M = 0.5, IFSAW, and legacy experimental techniques

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Fig. 8

h/h0: steady film cooling, M = 0.5

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Fig. 9

Adiabatic effectiveness: steady film cooling, M = 1.0

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Fig. 10

h/h0: steady film cooling, M = 1.0

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Fig. 11

Time-resolved η contours: asymmetric oscillation, M = 1.0

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Fig. 12

Time-resolved h/h0 contours: asymmetric oscillation, M = 1.0

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Fig. 13

Time-resolved NHFR contours: asymmetric oscillation, M = 1.0

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Fig. 14

Adiabatic effectiveness at x/d = 2: asymmetric oscillation, M = 1.0 (stagnation line over hole at 0 and 0.1 s)

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Fig. 15

h/h0 at x/d = 2: asymmetric oscillation, M = 1.0

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Fig. 16

NHFR at x/d = 2: asymmetric oscillation, M = 1.0

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Fig. 17

h/h0 at x/d = 2: symmetric oscillation, M = 0

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Fig. 18

Adiabatic effectiveness at x/d = 2: symmetric oscillation, M = 0.5

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Fig. 19

Adiabatic effectiveness at x/d = 2: symmetric oscillation, M = 1.0

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Fig. 20

h/h0 at x/d = 2: symmetric oscillation, M = 1.0

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Fig. 21

Average NHFR, symmetric oscillation, and steady stagnation, M = 1.0

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